Maximum rotor lift capability is investigated using wind-tunnel test data of McHugh (modified 1/10-scale CH-47B rotor) and a full-scale UH-60A rotor. Rotor performance calculations with the comprehensive rotorcraft analysis CAMRAD II are compared with the wind-tunnel test data. The analysis of the McHugh rotor with the Reynolds-number-corrected airfoil table shows good correlation with the measurements for μ=0.1 to 0.5 and is able to predict the maximum rotor lift reasonably well, especially at 0.2≤μ≤0.4. The analysis is also able to predict the maximum lift of the full-scale UH-60A rotor within about 3.5% at μ=0.24 and 0.3. Calculations with dynamic stall models, in general, show only a small influence on the rotor performance and are not necessary to predict maximum lift. Airfoils have an important role in defining the maximum lift capability of the rotor. The VR-12 airfoil, which has stall characteristics superior to the baseline V23010 airfoil, substantially improves the maximum lift capability of the McHugh rotor, showing the potential to improve the behavior of a rotor by improving the airfoil's static stall characteristics.
Prediction of Maximum Lift Capability of Helicopter Rotors
Journal of aircraft ; 52 , 1
2015
Aufsatz (Zeitschrift)
Englisch
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